TurboElectric Distributed Propulsion (TeDP) Design, Performance, Benefits, Concerns and Considerations for both Conventional Non-Superconducting and Cryogenically Cooled Superconducting Machines in a Propulsion System Architecture for Conventional Tube-and-Wing Configuration

摘要

TurboElectric propulsion consists of multiple components converting the fuel burned in the combustor of a turbine engine to thrust produced by a distribution of electric motor driven fans. Both conventional and cryogenically-cooled superconducting methods were analyzed. An inboard split-wing configuration has been studied during several NASA SBIR grants and other contracts with aerospace primes. These vehicles were developed during the "N+2 Distributed Electric Propulsion Studies", as a part of the NASA Ames Research Center for Environmentally Responsible Aviation (ERA) . In-house performance and sizing tools have been utilized, including DoeTECH and Hybrid Aircraft Propulsion System Synthesis (HAPSS). DoeTECH analyzes the hybrid system performance and HAPSS sizes the electric propulsion system for the aircraft, including the fan design, motor, turbine, and generator. The design and integration of the distributed turboelectric propulsion system has been addressed, including inlet, fan, and nozzle designs, as well as structural implications. Initial qualitative CFD studies have accompanied these designs.